EP2449265A1 - Propeller hub - Google Patents

Propeller hub

Info

Publication number
EP2449265A1
EP2449265A1 EP10726997A EP10726997A EP2449265A1 EP 2449265 A1 EP2449265 A1 EP 2449265A1 EP 10726997 A EP10726997 A EP 10726997A EP 10726997 A EP10726997 A EP 10726997A EP 2449265 A1 EP2449265 A1 EP 2449265A1
Authority
EP
European Patent Office
Prior art keywords
ring
plates
hub
turbomachine
radial
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP10726997A
Other languages
German (de)
French (fr)
Other versions
EP2449265B1 (en
Inventor
Eric Jacques Boston
Michel André BOURU
Laurent Jablonski
Philippe Gérard Edmond JOLY
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2449265A1 publication Critical patent/EP2449265A1/en
Application granted granted Critical
Publication of EP2449265B1 publication Critical patent/EP2449265B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/306—Blade pitch-changing mechanisms specially adapted for contrarotating propellers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a propeller hub with variable pitch blades for a turbomachine type unvented fan (in English "open rotor” or “unducted fan”).
  • the blower of a turbomachine of this type typically comprises two coaxial and contra-rotating external propellers, respectively upstream and downstream, which are each driven in rotation by a turbine of the turbomachine and which extend substantially radially outwardly of the engine nacelle. this turbomachine.
  • Each helix comprises a hub comprising a polygonal ring with substantially radial cylindrical housings distributed around the longitudinal axis of the turbomachine and in which are the blades of the propeller.
  • the hub further includes a rotor member of the turbine and a holding flange connecting the polygonal ring to the rotor member.
  • the blades can rotate in the housings of the polygonal ring and are rotated about the axes of the blades by appropriate means so as to adjust the angular setting of the blades, and to optimize it depending on the operating conditions of the turbomachine .
  • the blades of the propeller are subjected to very large centrifugal forces of up to 30,000 daN, these forces being transmitted to the polygonal ring. In case of rupture of the polygonal ring, the blades could be released, causing considerable structural damage around the turbomachine.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a propeller hub with variable pitch blades for a turbomachine comprising a polygonal ring with substantially radial cylindrical housings distributed around a central axis of the ring to receive said blades, an element of turbine rotor of the turbomachine, and a holding flange attached to the ring to connect it to the rotor element, and a plurality of rescue retention hooks received with clearance in orifices, the retention hooks of relief being tied to one of the ring or rotor element, and the orifices to the other.
  • said emergency retention hooks take up the radial force, thereby ensuring at least the retention of the ring and limiting the potential damage of this ring. failure.
  • said emergency retention hooks are held by radial plates capable of being fixed to said rotor element.
  • each radial plate carries at least two keys, having a substantially circular section, forming emergency retention hooks.
  • said emergency retention hooks have a non-round section, just as said orifices.
  • said emergency retention hooks may be attached to said radial plates or may be formed integrally with said plates.
  • the emergency retention hooks limit as much the translation as the rotation of a sector of the polygonal ring relative to the corresponding radial plate in a radial plane of the polygonal ring.
  • said holding flange is fixed on one side of the ring, and said plates are placed on one side axially opposite the ring, so as to limit the axial displacement of the ring.
  • said hub further comprises means for axially fixing said hooks in a direction parallel to the central axis of the ring, such as, for example, bolts connecting the plates to the rotor element oriented parallel to the axis. central of the ring.
  • said plates comprise a relief allowing a positive engagement in a radial plane with a support of said plates.
  • This positive engagement thus blocks the displacement of the plates in a radial plane as long as the plates are held against their support by said axial fixing means.
  • This engagement may for example be formed by a central projection in the support engaging a central notch in the plate, and two lateral projections in the support each engaging a side edge of the plate.
  • FIG. 1 illustrates a turbomachine of the unfired propeller type.
  • FIG. 2 is a perspective view of a polygonal ring for retention of unveined propeller blades according to the state of the art.
  • Figure 3 shows a front view of the polygonal ring of a propeller hub according to a first embodiment of the invention.
  • Figure 4 shows a front view of the polygonal ring of a propeller hub according to a second embodiment of the invention.
  • FIG. 5 shows a detailed view of the polygonal ring of FIG. 3 attached to a turbomachine rotor element.
  • FIG. 6 shows a detailed view of the polygonal ring of FIG. 4 fixed on a turbomachine rotor element.
  • FIG. 7 shows a partial longitudinal section of the polygonal ring of FIG. 3 fixed on a turbomachine rotor element.
  • FIG. 8 shows a partial longitudinal section of the polygonal ring of FIG. 4 fixed on a turbomachine rotor element.
  • FIG. 1 shows a turbomachine 10 with a non-ducted fan (in English "open rotor” or
  • Unducted fan which comprises, from upstream to downstream, in the direction of flow of the gases inside the turbomachine, a compressor
  • Each of these downstream turbines 18, 20 is integral in rotation with an external helix 22, 24 extending radially outside the nacelle 26 of the turbomachine, this nacelle 26 being substantially cylindrical and extending along the outside.
  • the flow of air 28 which enters the turbomachine is compressed and is mixed with fuel and burned in the combustion chamber 14, the combustion gases then passing into the turbines to rotate the propellers 22, 24 which provide the major part of the thrust generated by the turbomachine.
  • the combustion gases leaving the turbines are expelled through a nozzle 32 (arrows 30) to increase the thrust.
  • the propellers 22, 24 are arranged coaxially one behind the other and comprise a plurality of blades regularly distributed around the axis A of the turbomachine. These blades extend substantially radially and are of the variable-pitch type, that is to say that they can rotate about their axes so as to optimize their angular position depending on the operating conditions of the turbomachine.
  • each helix comprises a rotor element formed by a polygonal ring which extends around the axis A and which comprises a plurality of substantially cylindrical radial housings in which are engaged means for mounting the blades of the rotor. propeller.
  • a polygonal ring 134 is illustrated in FIG. 2. It comprises cylindrical housings 136 which are substantially radial and which have cylindrical walls 156 and a plurality of recesses 158 regularly distributed around the central axis C of the ring and formed in the form ring to lighten it. Each recess 158 is located between two consecutive radial housings 136.
  • Such a polygonal ring 134 forms a critical point of failure for the turbomachine.
  • the propeller blades could be released and, driven by the centrifugal forces, generate very significant damage around the turbomachine. Measures must therefore be taken to prevent this risk.
  • FIG. 3 A polygonal ring 234 forming part of a helical hub according to a first embodiment of the invention is illustrated in FIG. 3. Like the ring 134, this ring 234 also comprises cylindrical housings 236 distributed radially around the outside. ring to receive the blades. However, this ring 234 also has radial projections 240 distributed radially around the ring and each having two orifices 241 cylindrical and substantially parallel to the central axis C of the ring. These radial projections 240 are interposed between the cylindrical housings 236, so as not to interfere with them. Referring to FIG.
  • the propeller hub according to this first embodiment of the invention comprises radial plates 242 intended to be connected to a turbine rotor element 243, and each carrying two round section keys 244. received with clearance in the two orifices 241 of a radial projection 240 of the ring 234. the keys form emergency retention hooks.
  • the ring 234 is connected to the rotor element 243 by a holding flange 245.
  • This holding flange 245 is fixed to the rotor element 243 by bolts 246, and to the ring 234, on a side axially opposite the radial plates 242, by bolts 247.
  • the radial plates 242 are attached to the rotor element
  • the rotor element 243 by the same bolts 246 fixing the holding flange 245. These bolts 246 substantially oriented in the direction of the central axis C of the ring 234.
  • the rotor element 243 has, for each plate 242, a central projection 248 engaging a central notch 249 in the plate 242, and two side projections 250 each contacting a side edge 251 of the plate 242.
  • these projections in the rotor member 243 form a positive engagement with the plate 242 in a plane radial perpendicular to the central axis of the ring 234.
  • each plate 242 carries two keys 244 and is in positive engagement in the radial plane with the rotor element 243, the Plates 242 can transmit not only forces, but also local torques in the radial plane to said rotor element 243. In this way, the plates 242 provide additional security against the rupture of the propeller hub according to the invention.
  • the emergency retention hooks of the polygonal ring 334 are not formed by pairs of round section keys, but by lateral projections 344 of the radial plates 342 in the direction of the central axis C of the Polygonal ring 334.
  • the lateral projections 344 form a single piece with the plates 342. These lateral projections 344, whose section is rectangular, are received with clearance in orifices 341 with elongated section in radial projections 340 of the ring 336. .
  • the ring 334 is connected to the rotor element 343 by a holding flange 345.
  • This holding flange 345 is attached to the rotor member 343 by bolts 346, and to the ring 334, on a side axially opposite the radial plates 342, by bolts 347.
  • the radial plates 342 are fixed to the rotor element 343 by the same bolts 346 fixing the holding flange 345, bolts 346 substantially oriented in the direction of the central axis C of the ring 334.
  • the element rotor 343 has, for each plate 342, a central projection 348 engaging a central notch 349 in the plate 342, and two lateral projections 350 each contacting a lateral edge 351 of the plate 342.
  • these projections in the rotor element 343 form a positive engagement with the plate 342 in a radial plane perpendicular to the central axis of the ring 334.
  • the plates 342 ensure the retention of the ring 334 in case of rupture or substantial radial deformation of the ring 336 and / or the flange 345.
  • the local pairs in the radial plane are transmitted from the ring 334 to the plates 342 by the non-round section of the projections 344 and orifices 341.
  • radial plate could be placed between two adjacent radial housings in the polygonal ring. Some radial plates could be placed on the same side as the attachments of the polygonal ring to the holding flange, alternating said fasteners and plates.
  • the emergency retention means could also be coupled to the ring rather than to the rotor element, and the orifices receiving them then be coupled to the rotor element rather than to the ring. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a hub of a propeller with variable-pitch blades for a turbine engine, in particular for a propfan engine. The hub of the propeller comprises a polygonal ring (234) with substantially radial cylindrical recesses (236) distributed about a central axis of the ring (234) for receiving said blades, a turbine rotor element (243) of the turbine engine, and a securing flange that is attached to the ring so as to connect said ring to said rotor element (243). The hub further comprises a plurality of back-up hooks (244) inserted with clearance in openings (241), the back-up hooks (244) being connected either to the ring (234) or to the rotor element (243), and the openings (241) being connected to the other one of the two.

Description

MOYEU D'HELICE  PROPELLER HUB
La présente invention concerne un moyeu d'hélice à pales à calage variable pour une turbomachine du type à soufflante non carénée (en anglais « open rotor » ou « unducted fan »).  The present invention relates to a propeller hub with variable pitch blades for a turbomachine type unvented fan (in English "open rotor" or "unducted fan").
La soufflante d'une turbomachine de ce type comprend typiquement deux hélices externes coaxiales et contrarotatives, respectivement amont et aval, qui sont chacune entraînées en rotation par une turbine de la turbomachine et qui s'étendent sensiblement radialement à l'extérieur de la nacelle de cette turbomachine.  The blower of a turbomachine of this type typically comprises two coaxial and contra-rotating external propellers, respectively upstream and downstream, which are each driven in rotation by a turbine of the turbomachine and which extend substantially radially outwardly of the engine nacelle. this turbomachine.
Chaque hélice comprend un moyeu comportant un anneau polygonal avec des logements cylindriques sensiblement radiaux répartis autour de l'axe longitudinal de la turbomachine et dans lesquels sont les pales de l'hélice. Le moyeu comporte en outre un élément de rotor de la turbine et une bride de maintien reliant l'anneau polygonal à l'élément de rotor.  Each helix comprises a hub comprising a polygonal ring with substantially radial cylindrical housings distributed around the longitudinal axis of the turbomachine and in which are the blades of the propeller. The hub further includes a rotor member of the turbine and a holding flange connecting the polygonal ring to the rotor member.
Les pales peuvent tourner dans les logements de l'anneau polygonal et sont entraînées en rotation autour des axes des pales par des moyens appropriés de façon à régler le calage angulaire des pales, et à l'optimiser en fonction des conditions de fonctionnement de la turbomachine.  The blades can rotate in the housings of the polygonal ring and are rotated about the axes of the blades by appropriate means so as to adjust the angular setting of the blades, and to optimize it depending on the operating conditions of the turbomachine .
En fonctionnement, les pales de l'hélice sont soumises à des forces centrifuges très importantes pouvant atteindre 30 000 daN, ces forces étant transmises à l'anneau polygonal. En cas de rupture de l'anneau polygonal, les pales pourraient se libérer, causant des dommages structuraux très importants autour de la turbomachine.  In operation, the blades of the propeller are subjected to very large centrifugal forces of up to 30,000 daN, these forces being transmitted to the polygonal ring. In case of rupture of the polygonal ring, the blades could be released, causing considerable structural damage around the turbomachine.
L'invention a notamment pour but d'apporter une solution simple, efficace et économique à ce problème.  The invention aims in particular to provide a simple, effective and economical solution to this problem.
Elle a pour objet un moyeu d'hélice du type précité intégrant une sécurité contre les défaillances de l'anneau polygonal. Elle propose à cet effet un moyeu d'hélice à pales à calage variable pour une turbomachine, le moyeu comportant un anneau polygonal avec des logements cylindriques sensiblement radiaux répartis autour d'un axe central de l'anneau pour recevoir lesdites pales, un élément de rotor de turbine de la turbomachine, et une bride de maintien fixée à l'anneau de manière à le relier à l'élément de rotor, et une pluralité de crochets de rétention de secours reçus avec jeu dans des orifices, les crochets de rétention de secours étant liés à l'un de l'anneau ou de l'élément de rotor, et les orifices à l'autre. It relates to a propeller hub of the aforementioned type incorporating a security against the failures of the polygonal ring. It proposes for this purpose a propeller hub with variable pitch blades for a turbomachine, the hub comprising a polygonal ring with substantially radial cylindrical housings distributed around a central axis of the ring to receive said blades, an element of turbine rotor of the turbomachine, and a holding flange attached to the ring to connect it to the rotor element, and a plurality of rescue retention hooks received with clearance in orifices, the retention hooks of relief being tied to one of the ring or rotor element, and the orifices to the other.
En cas de rupture ou déformation radiale de l'anneau polygonal et/ou de la bride de maintien, lesdits crochets de rétention de secours reprennent l'effort radial, assurant ainsi au moins la rétention de l'anneau et limitant les dégâts potentiels de cette défaillance.  In the event of rupture or radial deformation of the polygonal ring and / or the holding flange, said emergency retention hooks take up the radial force, thereby ensuring at least the retention of the ring and limiting the potential damage of this ring. failure.
Avantageusement, lesdits crochets de rétention de secours sont tenus par des plaques radiales aptes à être fixées audit élément de rotor.  Advantageously, said emergency retention hooks are held by radial plates capable of being fixed to said rotor element.
Dans un premier mode de réalisation chaque plaque radiale porte au moins deux clavettes, ayant une section sensiblement circulaire, formant des crochets de rétention de secours.  In a first embodiment each radial plate carries at least two keys, having a substantially circular section, forming emergency retention hooks.
Dans un deuxième mode de réalisation, lesdits crochets de rétention de secours présentent une section non-ronde, tout comme lesdits orifices.  In a second embodiment, said emergency retention hooks have a non-round section, just as said orifices.
Dans un cas comme dans l'autre, lesdits crochets de rétention de secours peuvent être rapportés sur lesdites plaques radiales ou bien être formés d'une seule pièce avec lesdites plaques.  In either case, said emergency retention hooks may be attached to said radial plates or may be formed integrally with said plates.
Dans les deux cas, les crochets de rétention de secours limitent autant la translation que la rotation d'un secteur de l'anneau polygonal par rapport à la plaque radiale correspondante dans un plan radial de l'anneau polygonal.  In both cases, the emergency retention hooks limit as much the translation as the rotation of a sector of the polygonal ring relative to the corresponding radial plate in a radial plane of the polygonal ring.
Avantageusement, ladite bride de maintien est fixée sur un côté de l'anneau, et lesdites plaques sont placées d'un coté axialement opposé à l'anneau, de manière à limiter le déplacement axial de l'anneau. Advantageously, said holding flange is fixed on one side of the ring, and said plates are placed on one side axially opposite the ring, so as to limit the axial displacement of the ring.
Avantageusement, ledit moyeu comporte en outre des moyens de fixation axiaux desdits crochets dans une direction parallèle à l'axe central de l'anneau, tels que, par exemple des boulons reliant les plaques à l'élément de rotor orientés parallèlement à l'axe central de l'anneau.  Advantageously, said hub further comprises means for axially fixing said hooks in a direction parallel to the central axis of the ring, such as, for example, bolts connecting the plates to the rotor element oriented parallel to the axis. central of the ring.
Plus particulièrement, lesdites plaques comportent un relief permettant un engagement positif dans un plan radial avec un support desdites plaques. Cet engagement positif bloque ainsi le déplacement des plaques dans un plan radial tant que les plaques sont retenues contre leur support par lesdits moyens de fixation axiaux. Cet engagement peut par exemple être formé par une saillie centrale dans le support engageant une encoche centrale dans la plaque, et deux saillies latérales dans le support engageant chacune un bord latéral de la plaque.  More particularly, said plates comprise a relief allowing a positive engagement in a radial plane with a support of said plates. This positive engagement thus blocks the displacement of the plates in a radial plane as long as the plates are held against their support by said axial fixing means. This engagement may for example be formed by a central projection in the support engaging a central notch in the plate, and two lateral projections in the support each engaging a side edge of the plate.
Des détails concernant l'invention sont décrits ci-après faisant référence aux dessins.  Details of the invention are described below with reference to the drawings.
La figure 1 illustre une turbomachine du type à hélices non carénées.  FIG. 1 illustrates a turbomachine of the unfired propeller type.
La figure 2 illustre en perspective un anneau polygonal de rétention de pales d'hélices non carénées suivant l'état de la technique.  FIG. 2 is a perspective view of a polygonal ring for retention of unveined propeller blades according to the state of the art.
La figure 3 montre une vue de face de l'anneau polygonal d'un moyeu d'hélice suivant un premier mode de réalisation de l'invention.  Figure 3 shows a front view of the polygonal ring of a propeller hub according to a first embodiment of the invention.
La figure 4 montre une vue de face de l'anneau polygonal d'un moyeu d'hélice suivant un deuxième mode de réalisation de l'invention.  Figure 4 shows a front view of the polygonal ring of a propeller hub according to a second embodiment of the invention.
La figure 5 montre une vue de détail de l'anneau polygonal de là figure 3 fixé sur un élément de rotor de turbomachine. La figure 6 montre une vue de détail de l'anneau polygonal de la figure 4 fixé sur un élément de rotor de turbomachine. FIG. 5 shows a detailed view of the polygonal ring of FIG. 3 attached to a turbomachine rotor element. FIG. 6 shows a detailed view of the polygonal ring of FIG. 4 fixed on a turbomachine rotor element.
La figure 7 montre une coupe longitudinale partielle de l'anneau polygonal de la figure 3 fixé sur un élément de rotor de turbomachine.  FIG. 7 shows a partial longitudinal section of the polygonal ring of FIG. 3 fixed on a turbomachine rotor element.
La figure 8 montre une coupe longitudinale partielle de l'anneau polygonal de la figure 4 fixé sur un élément de rotor de turbomachine.  FIG. 8 shows a partial longitudinal section of the polygonal ring of FIG. 4 fixed on a turbomachine rotor element.
On se réfère d'abord à la figure 1 qui représente une turbomachine 10 à soufflante non carénée (en anglais « open rotor » ou Reference is first made to FIG. 1, which shows a turbomachine 10 with a non-ducted fan (in English "open rotor" or
« unducted fan ») qui comporte d'amont en aval, dans le sens d'écoulement des gaz à l'intérieur de la turbomachine, un compresseur"Unducted fan") which comprises, from upstream to downstream, in the direction of flow of the gases inside the turbomachine, a compressor
12, une chambre annulaire de combustion 14, une turbine haute pression12, an annular combustion chamber 14, a high pressure turbine
16, et deux turbines basse pression 18, 20 qui sont contrarotatives, c'est- à-dire qu'elles tournent dans deux sens opposés autour de l'axe longitudinal A de la turbomachine. 16, and two low-pressure turbines 18, 20 which are counter-rotating, that is to say they rotate in two opposite directions about the longitudinal axis A of the turbomachine.
Chacune de ces turbines aval 18, 20 est solidaire en rotation d'une hélice externe 22, 24 s'étendant radialement à l'extérieur de la nacelle 26 de la turbomachine, cette nacelle 26 étant sensiblement cylindrique et s'étendant le long de l'axe A autour du compresseur 12, de la chambre de combustion 14, et des turbines 16, 18 et 20.  Each of these downstream turbines 18, 20 is integral in rotation with an external helix 22, 24 extending radially outside the nacelle 26 of the turbomachine, this nacelle 26 being substantially cylindrical and extending along the outside. axis A around the compressor 12, the combustion chamber 14, and the turbines 16, 18 and 20.
Le flux d'air 28 qui pénètre dans la turbomachine est comprimé puis est mélangé à du carburant et brûlé dans la chambre de combustion 14, les gaz de combustion passant ensuite dans les turbines pour entraîner en rotation les hélices 22, 24 qui fournissent la majeure partie de la poussée générée par la turbomachine. Les gaz de combustion sortant des turbines sont expulsés à travers une tuyère 32 (flèches 30) pour augmenter la poussée.  The flow of air 28 which enters the turbomachine is compressed and is mixed with fuel and burned in the combustion chamber 14, the combustion gases then passing into the turbines to rotate the propellers 22, 24 which provide the major part of the thrust generated by the turbomachine. The combustion gases leaving the turbines are expelled through a nozzle 32 (arrows 30) to increase the thrust.
Les hélices 22, 24 sont disposées coaxialement l'une derrière l'autre et comportent une pluralité de pales régulièrement réparties autour de l'axe A de la turbomachine. Ces pales s'étendent sensiblement radialement et sont du type à calage variable, c'est-à-dire qu'elles peuvent tourner autour de leurs axes de façon à optimiser leur position angulaire en fonction des conditions de fonctionnement de la turbomachine. The propellers 22, 24 are arranged coaxially one behind the other and comprise a plurality of blades regularly distributed around the axis A of the turbomachine. These blades extend substantially radially and are of the variable-pitch type, that is to say that they can rotate about their axes so as to optimize their angular position depending on the operating conditions of the turbomachine.
Dans un montage précédent, chaque hélice comprend un élément de rotor formé par un anneau polygonal qui s'étend autour de l'axe A et qui comporte une pluralité de logements radiaux sensiblement cylindriques dans lesquels sont engagés des moyens de montage des pales de l'hélice. Un tel anneau polygonal 134 est illustré sur la figure 2. Il comprend des logements cylindriques 136 sensiblement radiaux et présentant des parois cylindriques 156 et une pluralité d'évidements 158 régulièrement répartis autour de l'axe central C de l'anneau et formés dans l'anneau pour l'alléger. Chaque évidement 158 est situé entre deux logements radiaux 136 consécutifs.  In a previous arrangement, each helix comprises a rotor element formed by a polygonal ring which extends around the axis A and which comprises a plurality of substantially cylindrical radial housings in which are engaged means for mounting the blades of the rotor. propeller. Such a polygonal ring 134 is illustrated in FIG. 2. It comprises cylindrical housings 136 which are substantially radial and which have cylindrical walls 156 and a plurality of recesses 158 regularly distributed around the central axis C of the ring and formed in the form ring to lighten it. Each recess 158 is located between two consecutive radial housings 136.
Un tel anneau polygonal 134 forme un point de défaillance critique pour la turbomachine. En cas de rupture de l'anneau polygonal 134 ou de sa liaison avec la turbine, les pales d'hélice pourraient se libérer et, impulsées par les forces centrifuges, générer des dommages très importants autour de la turbomachine. Des mesures doivent donc être prises pour prévenir ce risque.  Such a polygonal ring 134 forms a critical point of failure for the turbomachine. In case of rupture of the polygonal ring 134 or its connection with the turbine, the propeller blades could be released and, driven by the centrifugal forces, generate very significant damage around the turbomachine. Measures must therefore be taken to prevent this risk.
Un anneau polygonal 234 formant partie d'un moyeu d'hélice suivant un premier mode de réalisation de l'invention est illustré sur la figure 3. Comme l'anneau 134, cet anneau 234 comporte aussi des logements cylindriques 236 distribués radialement autour de l'anneau afin de recevoir les pales. Toutefois, cet anneau 234 comporte aussi des saillies radiales 240 distribuées radialement autour de l'anneau et présentant chacune deux orifices 241 cylindriques et sensiblement parallèles à l'axe central C de l'anneau. Ces saillies radiales 240 sont intercalées entre les logements cylindriques 236, de manière à ne pas interférer avec ceux-ci . En se reportant vers la figure 5, le moyeu d'hélice suivant ce premier mode de réalisation de l'invention comporte des plaques radiales 242 destinées à être connectées à un élément de rotor de turbine 243, et portant chacune deux clavettes 244 à section ronde reçues avec jeu dans les deux orifices 241 d'une saillie radiale 240 de l'anneau 234. les clavettes forment des crochets de rétention de secours. A polygonal ring 234 forming part of a helical hub according to a first embodiment of the invention is illustrated in FIG. 3. Like the ring 134, this ring 234 also comprises cylindrical housings 236 distributed radially around the outside. ring to receive the blades. However, this ring 234 also has radial projections 240 distributed radially around the ring and each having two orifices 241 cylindrical and substantially parallel to the central axis C of the ring. These radial projections 240 are interposed between the cylindrical housings 236, so as not to interfere with them. Referring to FIG. 5, the propeller hub according to this first embodiment of the invention comprises radial plates 242 intended to be connected to a turbine rotor element 243, and each carrying two round section keys 244. received with clearance in the two orifices 241 of a radial projection 240 of the ring 234. the keys form emergency retention hooks.
Comme illustré sur la figure 7, l'anneau 234 est lié à l'élément de rotor 243 par une bride de maintien 245. Cette bride de maintien 245 est fixée à l'élément de rotor 243 par des boulons 246, et à l'anneau 234, sur un côté axialement opposé aux plaques radiales 242, par des boulons 247.  As illustrated in FIG. 7, the ring 234 is connected to the rotor element 243 by a holding flange 245. This holding flange 245 is fixed to the rotor element 243 by bolts 246, and to the ring 234, on a side axially opposite the radial plates 242, by bolts 247.
Les plaques radiales 242 sont fixées à l'élément de rotor The radial plates 242 are attached to the rotor element
243 par les mêmes boulons 246 fixant la bride de maintien 245. Ces boulons 246 sensiblement orientés dans la direction de l'axe central C de l'anneau 234. En outre, l'élément de rotor 243 présente, pour chaque plaque 242, une saillie centrale 248 engageant une encoche centrale 249 dans la plaque 242, et deux saillies latérales 250 contactant chacune un bord latéral 251 de la plaque 242. Ainsi ces saillies dans l'élément de rotor 243 forment un engagement positif avec la plaque 242 dans un plan radial perpendiculaire à l'axe central de l'anneau 234. 243 by the same bolts 246 fixing the holding flange 245. These bolts 246 substantially oriented in the direction of the central axis C of the ring 234. In addition, the rotor element 243 has, for each plate 242, a central projection 248 engaging a central notch 249 in the plate 242, and two side projections 250 each contacting a side edge 251 of the plate 242. Thus, these projections in the rotor member 243 form a positive engagement with the plate 242 in a plane radial perpendicular to the central axis of the ring 234.
En fonctionnement normal, comme les clavettes 244 sont reçues avec jeu dans les orifices 241 , aucun effort n'est transmis à travers les plaques 242. Tous les efforts de l'anneau 234 vers l'élément de rotor 243 sont transmis par la bride de maintien 245. Cependant, en cas de rupture ou déformation radiale sensible de l'anneau 234 et/ou de la bride de maintien 245, les clavettes 244 contactent les parois des orifices 241 et reprennent au moins une partie des efforts radiaux de rétention d'au moins une section de l'anneau 236. Les clavettes 244 forment ainsi des crochets de rétention de secours de l'anneau 236. Comme chaque plaque 242 porte deux clavettes 244 et est en engagement positif dans le plan radial avec l'élément de rotor 243, les plaques 242 peuvent transmettre audit élément de rotor 243 non seulement des forces, mais aussi des couples locaux dans le plan radial. De cette manière, les plaques 242 offrent une sécurité additionnelle contre la rupture du moyeu d'hélice suivant l'invention. In normal operation, as the keys 244 are received with clearance in the orifices 241, no force is transmitted through the plates 242. All the forces of the ring 234 towards the rotor element 243 are transmitted by the flange of 245. However, in case of rupture or substantial radial deformation of the ring 234 and / or the holding flange 245, the wedges 244 contact the walls of the orifices 241 and take up at least part of the radial retention efforts of at least one section of the ring 236. The keys 244 thus form emergency retention hooks of the ring 236. As each plate 242 carries two keys 244 and is in positive engagement in the radial plane with the rotor element 243, the Plates 242 can transmit not only forces, but also local torques in the radial plane to said rotor element 243. In this way, the plates 242 provide additional security against the rupture of the propeller hub according to the invention.
Dans un autre mode de réalisation illustré sur les figures 4, In another embodiment illustrated in FIGS.
6 et 8, les crochets de rétention de secours de l'anneau polygonal 334 ne sont pas formés par des paires de clavettes à section ronde, mais par des saillies latérales 344 des plaques radiales 342 dans la direction de l'axe central C de l'anneau polygonal 334. Les saillies latérales 344 forment une seule pièce avec les plaques 342. Ces saillies latérales 344, dont la section est rectangulaire, sont reçues avec jeu dans des orifices 341 à section allongée dans des saillies radiales 340 de l'anneau 336. 6 and 8, the emergency retention hooks of the polygonal ring 334 are not formed by pairs of round section keys, but by lateral projections 344 of the radial plates 342 in the direction of the central axis C of the Polygonal ring 334. The lateral projections 344 form a single piece with the plates 342. These lateral projections 344, whose section is rectangular, are received with clearance in orifices 341 with elongated section in radial projections 340 of the ring 336. .
Tel qu'il est illustré sur la figure 6 et de manière analogue au premier mode de réalisation, l'anneau 334 est lié à l'élément de rotor 343 par une bride de maintien 345. Cette bride de maintien 345 est fixée à l'élément de rotor 343 par des boulons 346, et à l'anneau 334, sur un côté axialement opposé aux plaques radiales 342, par des boulons 347.  As illustrated in FIG. 6 and in a similar manner to the first embodiment, the ring 334 is connected to the rotor element 343 by a holding flange 345. This holding flange 345 is attached to the rotor member 343 by bolts 346, and to the ring 334, on a side axially opposite the radial plates 342, by bolts 347.
Les plaques radiales 342 sont fixées à l'élément de rotor 343 par les mêmes boulons 346 fixant la bride de maintien 345, boulons 346 sensiblement orientés dans la direction de l'axe central C de l'anneau 334. En outre, l'élément de rotor 343 présente, pour chaque plaque 342, une saillie centrale 348 engageant une encoche centrale 349 dans la plaque 342, et deux saillies latérales 350 contactant chacune un bord latéral 351 de la plaque 342. Ainsi ces saillies dans l'élément de rotor 343 forment un engagement positif avec la plaque 342 dans un plan radial perpendiculaire à l'axe central de l'anneau 334.  The radial plates 342 are fixed to the rotor element 343 by the same bolts 346 fixing the holding flange 345, bolts 346 substantially oriented in the direction of the central axis C of the ring 334. In addition, the element rotor 343 has, for each plate 342, a central projection 348 engaging a central notch 349 in the plate 342, and two lateral projections 350 each contacting a lateral edge 351 of the plate 342. Thus these projections in the rotor element 343 form a positive engagement with the plate 342 in a radial plane perpendicular to the central axis of the ring 334.
Comme dans le premier mode de réalisation de l'invention, les plaques 342 assurent la rétention de l'anneau 334 en cas de rupture ou déformation radiale sensible de l'anneau 336 et/ou la bride 345. Dans ce mode de réalisation, les couples locaux dans le plan radial sont transmis de l'anneau 334 aux plaques 342 par la section non-ronde des saillies 344 et des orifices 341. As in the first embodiment of the invention, the plates 342 ensure the retention of the ring 334 in case of rupture or substantial radial deformation of the ring 336 and / or the flange 345. In this embodiment, the local pairs in the radial plane are transmitted from the ring 334 to the plates 342 by the non-round section of the projections 344 and orifices 341.
Quoique la présente invention ait été décrite par référence à des exemples de réalisation spécifiques, il est évident que des différentes modifications et changements peuvent être effectués sur ces exemples sans sortir de la portée générale de l'invention telle que définie par les revendications. Par exemple, plus d'une plaque radiale pourrait être placée entre deux logements radiaux adjacents dans l'anneau polygonal. Certaines plaques radiales pourraient placées du même côté que les fixations de l'anneau polygonal à la bride de maintien, en alternant lesdites fixations et les plaques. Les moyens de rétention de secours pourraient aussi être couplés à l'anneau plutôt qu'à l'élément de rotor, et les orifices les recevant être alors couplés à l'élément de rotor plutôt qu'à l'anneau. Par conséquent, la description et les dessins doivent être considérés dans un sens illustratif plutôt que restrictif.  Although the present invention has been described with reference to specific exemplary embodiments, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. For example, more than one radial plate could be placed between two adjacent radial housings in the polygonal ring. Some radial plates could be placed on the same side as the attachments of the polygonal ring to the holding flange, alternating said fasteners and plates. The emergency retention means could also be coupled to the ring rather than to the rotor element, and the orifices receiving them then be coupled to the rotor element rather than to the ring. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

Claims

REVENDICATIONS
1. Moyeu d'hélice à pales à calage variable pour une turbomachine, comportant :  1. Propeller hub with variable pitch blades for a turbomachine, comprising:
• un anneau polygonal (234,334) avec des logements cylindriques (236,336) sensiblement radiaux répartis autour d'un axe central A polygonal ring (234,334) with substantially radial cylindrical housings (236,336) distributed around a central axis
(C) de l'anneau (234) pour recevoir lesdites pales, (C) the ring (234) for receiving said blades,
• un élément de rotor (243,343) de turbine de la turbomachine, et A turbine rotor element (243, 433) of the turbomachine, and
• une bride de maintien (245,345) fixée à l'anneau de manière à le relier audit élément de rotor (243,343), A holding flange (245,345) attached to the ring so as to connect it to said rotor element (243,343),
caractérisé par le fait qu'il comporte en outre une pluralité de crochets de rétention de secours (244,344) reçus avec jeu dans des orifices (241 ,341 ), les crochets de rétention de secours (244,344) étant liés à l'un de l'anneau (234,334) ou de l'élément de rotor (243,343), et les orifices (241 ,341 ) à l'autre. characterized in that it further comprises a plurality of emergency retention hooks (244,344) received with clearance in orifices (241, 341), the emergency retention hooks (244,344) being connected to one of the ring (234,334) or rotor element (243,343), and the orifices (241, 341) to each other.
2. Moyeu selon la revendication 1 , dans lequel lesdits crochets de rétention de secours (244,344) sont tenus par des plaques radiales (242,342) fixées audit élément de rotor (243,343).  A hub according to claim 1, wherein said emergency retention hooks (244,344) are held by radial plates (242,342) attached to said rotor element (243,343).
3. Moyeu suivant la revendication 2, dans lequel chaque plaque radiale (242) porte au moins deux clavettes formant crochets de rétention de secours (244) et ayant une section sensiblement circulaire.  The hub of claim 2, wherein each radial plate (242) carries at least two backup retention hook keys (244) and having a substantially circular section.
4. Moyeu suivant la revendication 2, lesdits crochets de rétention de secours (344) présentent une section non-ronde, tout comme lesdits orifices (341 ).  4. Hub according to claim 2, said emergency retention hooks (344) have a non-round section, as said orifices (341).
5. Moyeu suivant la revendication 2, dans lequel ladite bride de maintien (245,345) est fixée sur un côté de l'anneau (234,334), et lesdites plaques (242,342) sont placées d'un coté axialement opposé dudit anneau (234,334).  A hub according to claim 2, wherein said holding flange (245,345) is attached to one side of the ring (234,334), and said plates (242,342) are located on an axially opposite side of said ring (234,334).
6. Moyeu suivant la revendication 2, comportant en outre des moyens de fixation (246,346) desdites plaques (242,342) dans une direction parallèle audit axe central (C) de l'anneau. The hub of claim 2, further comprising means (246,346) for securing said plates (242,342) in a direction parallel to said central axis (C) of the ring.
7. Moyeu suivant la revendication 6, dans lequel lesdites plaques (242,342) comportent un relief permettant un engagement positif dans un plan radial avec un support desdites plaques (242,342). The hub according to claim 6, wherein said plates (242,342) comprise a relief allowing a positive engagement in a radial plane with a support of said plates (242,342).
8. Hélice (22,24) comportant un moyeu suivant une quelconque des revendications précédentes, et des pales reçues dans les logements cylindriques (236,336).  8. Propeller (22,24) having a hub according to any one of the preceding claims, and blades received in the cylindrical housing (236,336).
9. Turbomachine (10) comportant au moins une hélice (22,24) suivant la revendication 8.  9. Turbomachine (10) having at least one propeller (22,24) according to claim 8.
l O.Turbomachine (10) suivant la revendication 9, comportant deux hélices (22,24) contrarotatives.  O.Turbomachine (10) according to claim 9, comprising two propellers (22,24) counter-rotating.
EP10726997.9A 2009-07-02 2010-07-02 Propeller hub Active EP2449265B1 (en)

Applications Claiming Priority (2)

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FR0954561A FR2947590B1 (en) 2009-07-02 2009-07-02 PROPELLER HUB
PCT/EP2010/059467 WO2011000943A1 (en) 2009-07-02 2010-07-02 Propeller hub

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EP2449265B1 EP2449265B1 (en) 2016-09-28

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CN (1) CN102472294A (en)
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GB201118386D0 (en) 2011-10-25 2011-12-07 Rolls Royce Plc A support ring for a rotary assembly
GB201211133D0 (en) 2012-06-22 2012-08-08 Rolls Royce Plc A catcher ring arrangement
FR2992677B1 (en) * 2012-07-02 2016-03-18 Snecma HUB FOR RADIAL HOUSING OF TURBOMACHINE PROPELLER RING WITH VARIABLE SHAFT AND ASSEMBLY COMPRISING SUCH HUB
FR3027947B1 (en) * 2014-10-31 2021-05-14 Snecma PROPELLER RING INCLUDING RADIAL HOUSINGS WITH OVOID SECTION
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FR2947590B1 (en) 2011-07-15
JP5722318B2 (en) 2015-05-20
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FR2947590A1 (en) 2011-01-07
BRPI1014012A2 (en) 2016-04-12
US20120099989A1 (en) 2012-04-26
RU2543364C2 (en) 2015-02-27
CA2766661A1 (en) 2011-01-06
RU2012103479A (en) 2013-08-10
CN102472294A (en) 2012-05-23
EP2449265B1 (en) 2016-09-28
US8926279B2 (en) 2015-01-06
WO2011000943A1 (en) 2011-01-06

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